Formation of stabilized oblique detonation waves in a combustor

Initiation and stabilization of oblique detonation waves (ODWs) are important to the successful application engines (ODEs), which, however, have been rarely studied under realistic combustor conditions. In this study, flow structures, characteristics potential thrust performance (under different combustor's geometries with ODW reflection locations) in a typical hydrogen-fueled ODE numerically by solving two-dimensional multi-species Reynolds-averaged conservation equations detailed hydrogen combustion mechanism. Results suggest that all waves/shock can be stabilized space-confined combustor, boundary layer separation induced ODW-boundary interaction is found crucial determining types mode combustor. Except for expected ODW-induced combustion, fast overdriven normal wave (NDW) may exist simultaneously (even up large extent, >73.7%). It demonstrated NDW attributed formation an effective aerodynamic convergent-divergent nozzle quickly accelerates subsonic behind supersonic, preventing downstream disturbances from propagating upstream. Benefiting chemical equilibrium shift caused expansion effect flow, more heat released compensate compression loss simulated shown not deteriorate significantly even percentage NDW-induced existing This work would beneficial future developments ODEs.